Any aircraft design is an iterative process, and the conceptual and preliminary design stages of the design process are prone to be object of many changes and hot fixes that require organization and methodical approaches. The main objective of this paper is to expose the main features added to this developing software tool, that will allow to shorten the time-frame of these two activities by using a MATLAB application that promptly iterates over performance and trim calculations of several rotorcraft configurations, using statistical weight distribution methods for centre of gravity estimation, linearisation of the balancing trim equations, and Blade Element Momentum Theory for trim and performance calculations, respectfully.